Modulated Compressor Air Cooling for Gas Turbine Combustor
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Solution Overview
Problem
Conventional gas turbine engines face inefficiencies due to fixed cooling air systems that provide excessive cooling during low-demand conditions, such as cruise, leading to reduced engine performance and increased energy consumption.
Innovation Solution
A modular cooling air system that includes a valve and controller to selectively modulate the flow of primary and auxiliary cooling air, ensuring a continuous minimum flow to the turbine while supplementing cooling air during high-demand conditions, thereby optimizing cooling based on operational conditions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If fixed geometry cooling circuits are used designed for extreme conditions, then turbine life is protected under maximum takeoff conditions, but excessive cooling air is consumed during cruise conditions reducing engine efficiency
Solution Approach 1:
The patent applies dynamics by replacing fixed geometry cooling circuits with variable geometry cooling circuits that can adjust their cooling air flow characteristics. The cooling system includes movable components such as adjustable vanes or deflectors that change the flow path and amount of cooling air delivered to turbine blades based on real-time operating conditions, enabling the system to provide adequate cooling during takeoff while reducing cooling air consumption during cruise to maintain engine efficiency
Solution Approach 2:
The patent implements parameter changes by varying the cooling air flow rate and temperature parameters according to operating conditions. The system monitors parameters such as turbine inlet temperature, engine speed, and load conditions, then dynamically adjusts the cooling air flow parameters through controllable valves, variable area openings, or adjustable flow paths to optimize the balance between turbine protection and engine efficiency across different operating regimes
2Reliability
If fixed amount of cooling air is provided to turbine, then turbine cooling needs are met during maximum takeoff, but engine performance deteriorates during cruise due to unnecessary cooling air consumption
Solution Approach 1:
The patent employs dynamics by incorporating controllable flow regulation mechanisms such as adjustable guide vanes, movable flow restrictors, or electronically controlled valves in the cooling air paths. These dynamic components allow the system to modulate cooling air delivery in real-time, providing full cooling capacity during maximum takeoff while reducing cooling air flow during cruise conditions to preserve engine performance and reduce parasitic losses
Solution Approach 2:
The patent implements feedback control by using sensors to monitor turbine temperature, engine operating parameters, and cooling air flow rates. This feedback information is processed by a control system that automatically adjusts the cooling air flow through controllable components to maintain appropriate cooling levels matched to actual turbine thermal conditions, preventing both over-cooling during cruise and under-cooling during takeoff
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
This solution enhances engine efficiency by reducing unnecessary cooling air usage during low-demand conditions, maintaining turbine health while improving overall engine performance and reducing energy consumption.
Implementation Method 1
The combustor may define a cooling passage that directs air toward the turbine rotor
Implementation Method 2
The valve may be configured to open and close selectively to allow and block fluid communication between the transfer passageway and the combustion chamber to modulate a flow of auxiliary cooling air
Data Source
AI summary
A gas turbine engine comprises a turbine, a combustor fluidly coupled to the turbine, and a cooling air system. The turbine includes including a turbine rotor having a shaft mounted for rotation about an axis of the gas turbine engine and a set of turbine blades coupled to the turbine rotor for rotation therewith. The combustor includes an outer combustor case and an inner combustor case that cooperate to define a combustion chamber. The cooling air system is configured to cool the turbine using air form the combustion chamber of the combustor.